EP3330485B1 - Système de pale de turbomachine - Google Patents

Système de pale de turbomachine Download PDF

Info

Publication number
EP3330485B1
EP3330485B1 EP17202370.7A EP17202370A EP3330485B1 EP 3330485 B1 EP3330485 B1 EP 3330485B1 EP 17202370 A EP17202370 A EP 17202370A EP 3330485 B1 EP3330485 B1 EP 3330485B1
Authority
EP
European Patent Office
Prior art keywords
blade
region
turbomachine
guide
arrangement according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17202370.7A
Other languages
German (de)
English (en)
Other versions
EP3330485A1 (fr
Inventor
Richard Scharl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3330485A1 publication Critical patent/EP3330485A1/fr
Application granted granted Critical
Publication of EP3330485B1 publication Critical patent/EP3330485B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a turbomachine blade arrangement, a turbomachine, in particular a gas turbine, with the turbomachine blade arrangement and a method for producing the turbomachine blade arrangement.
  • the own DE 10 2009 010 185 A1 proposes to provide a plurality of damping bodies in a cavity in an inner or outer ring of a blade cluster, which damping elements dissipate vibration energy with one another and with the cavity.
  • the or one or more of the bodies have an, in particular minimum or maximum, outer dimension which is at least 1 mm and / or at most 10 mm, in particular at most 5 mm, in particular at 20 ° C. .
  • the turbomachine blade arrangement has a one or more part (elastic) support structure which supports or supports the body or bodies in a resilient or elastic manner, in particular captivates or binds, or is provided or set up for this purpose is used or by which the body (s) is / are springily or elastically supported or supported or tied or tied.
  • a minimum wall thickness of the elastic support structure is at most 50%, in particular at most 10%, and / or at least 1% of a maximum external dimension of the body.
  • the effect, in particular kinematics and / or dynamics, of the body or bodies can be improved in one embodiment, for example their movement, in particular shock energy storage and the like.
  • a maximum translational play of movement of the or one or more of the bodies is at least 0.01 mm, in particular at least 0.1 mm, and / or at least 1% of a minimum outer dimension of this body and / or at most 10 mm, in particular at most 1 mm, and / or at most 100% of a maximum outer dimension of this body, in particular at 20 ° C.
  • the effect, in particular kinematics and / or dynamics, of the body or bodies can be (further) improved in one embodiment, for example impact (main) direction (s), maximum (movement) path length (s) and the like.
  • the effect, in particular dynamics, of the body or bodies can be (further) improved in one embodiment, for example butt contacts (more) varied and the like.
  • the blade has an airfoil for flow deflection and / or a blade root, via which the blade can be or is connected or connected to a housing or rotor of the turbomachine in a further development in a non-destructive or non-destructive manner.
  • the blade in particular its blade root, can be formed integrally with the housing or rotor, in particular as a so-called "BLISK".
  • a shroud is arranged, in particular, on the airfoil, in particular the end thereof facing and / or facing away from the blade root or - based on a main or machine (rotating) axis of the turbomachine - radially inside and / or outside (in each case) formed integrally with the airfoil or, in particular not detachably non-destructively, connected to it.
  • the complete guide for guiding the body or the body or a part of the guide is or is jointly, in particular integrally, in particular integral with the complete blade, in particular your airfoil and / or foot and / or shroud, or a part thereof, generatively manufactured.
  • the or one or more of the bodies in particular impulse bodies, (in each case) partially or completely together or together, in particular integrally, with the complete blade, in particular its Airfoil and / or base and / or shroud, or a part thereof generatively manufactured.
  • a region of the blade, guide, support structure or the body (s) which is jointly generatively produced can thus be a (real) part (area) in one embodiment or the complete blade, guide, support structure or be or designate the complete body (s). For this reason, in the present case, for a more compact representation, one speaks in particular of “at least one area”.
  • the body or bodies can advantageously be secured against loss in one embodiment.
  • advantageous, in particular complex blades, guides, support structures or bodies can be produced in this way and the effect, in particular kinematics and / or dynamics, of the body or bodies can be (further) improved, for example power transmissions, movement games and the like.
  • Generative or additive manufacturing comprises, in a manner known per se, manufacturing in layers by repeatedly arranging, in particular liquid and / or loose, in particular granular or powdery, starting material on a previously (solidified) layer and locally solidifying and / or at least partially connected to it, in particular chemically and / or physically, in particular by energy input, in particular thermally and / or electromagnetically, in particular optically, in particular by exposure, in particular by means of laser (light).
  • the area of the blade which is generatively produced together with the guide (area), support structure (area) or body (area (s)) has a contact surface which the body or bodies during operation of the blade has to reduce vibrations of the blade , in particular temporarily, in particular several times and / or abruptly, or who is provided or set up or used for this purpose.
  • the area of the blade and the area of the guide, the support structure and / or the or one or more of the body (s) that is generatively produced together with it have metal, in a further development they are made generatively from metal powder as the starting material.
  • the guide has one or more open cavities and / or one or more closed cavities, in which the one or more bodies are arranged or received with play in one or more degrees of freedom.
  • open cavities can advantageously be used to remove unconsolidated starting material, particularly in additive manufacturing.
  • closed cavities protect the body (s) against working fluid of the turbomachine and / or improve their dynamics, in particular aerodynamics.
  • a maximum outer dimension of the body or one or more of the bodies is (in each case) larger than a maximum inner dimension or clear width of a through opening of a wall of the open cavity, for example larger than an inner diameter of a circular through opening.
  • the body or bodies can be secured against loss in one embodiment, and non-solidified starting material can nevertheless advantageously be removed during additive manufacturing.
  • one or the maximum outer dimension of the body or one or more of the bodies is greater than a maximum movement play of this body in the guide, in particular in one or more translational degrees of freedom (s), in particular at least twice as large as the maximum (translational) movement play.
  • Such bodies which are large in relation to their maximum range of motion, can particularly advantageously reduce certain vibrations, in particular vibration modes.
  • one or the maximum external dimensions of the body or one or more of the bodies is smaller than a maximum movement play of this body in the guide, in particular in one or more translational ones Degree (s) of freedom, in particular at most half the size of the maximum (translational) movement.
  • Such bodies which are small in relation to their maximum range of motion, can particularly advantageously reduce other vibrations, in particular vibration modes.
  • the guide, support structure and / or body can be protected against working fluid of the turbomachine.
  • the cavity is or is closed by a further component, in particular a housing or a rotor, of the turbomachine, in particular in that the blade is or is attached to it, in particular non-destructively or non-destructively detachably.
  • FIG. 12 shows a portion of a turbomachine blade assembly of a gas turbine according to an embodiment of the present invention with a rotor blade or guide blade 10, of which in FIG Fig. 1 a section of an airfoil 11, a blade root 12 and a shroud 13 arranged thereon is shown.
  • the blade root 12 is arranged on a housing or rotor 2 and uses it to define a closed cavity 3.
  • a guide 50 for movably guiding a body 4 for reducing the vibration of the blade 10 by means of multiple butt contacts is arranged, which has an open cavity 51 in which the spherical body 4 with play in a translational (vertical in Fig. 1 ) and three rotational degrees of freedom is arranged, with part of the blade root 12 or shroud 13 having or forming a contact surface 14 for contacting the body 4.
  • the outer diameter of the spherical body 4 is larger than a maximum inner dimension or clear width of a through opening 52 of a wall 53 of the guide or the open cavity and also larger than a maximum movement play s of the body 4 in the guide 50 or cavity 51.
  • Fig. 2 shows in Fig. 1 correspondingly, a section of a turbomachine blade arrangement of a gas turbine according to a further embodiment of the present invention.
  • Features corresponding to one another are identified by identical reference numerals, so that reference is made to the above description and only differences will be discussed below.
  • the spherical body 4 is not supported in a guide, but in the cavity 3 by a thin-walled support structure 6 on the blade root 12 resiliently supported or tied, which together with blade 11, blade root 12, shroud 13, and (impulse) body 4 is or is generatively made of metal powder.
  • the body 4 can in turn be manufactured or arranged in the cavity 3 in a secure manner against loss.
  • the body 4 and the support structure 6 are in turn advantageously protected against working fluid of the gas turbine by the subsequent connection of the blade root 12 to the housing or rotor 2.
  • the body 4 of the embodiments of FIG Fig. 1 , 2nd instead of being arranged on a side of the blade root 12 facing away from the airfoil, it is also arranged in the airfoil 11 or an opposing (further) shroud (not shown) and for this purpose it is at least partially produced together with the guide or support structure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Système de pale de turbomachine, en particulier pour un étage de compresseur ou de turbine d'une turbine à gaz, lequel système comporte au moins une pale (10), en particulier une pale mobile ou directrice, et au moins un corps mobile (4) permettant de réduire les vibrations de ladite pale, caractérisé en ce qu'au moins une zone d'un guide (50) pour le guidage du corps et/ou au moins une zone d'une structure de support (6) pour le montage élastique du corps et/ou au moins une zone du corps (4) conjointement avec au moins une zone de la pale (10), en particulier d'une lame (11) et/ou d'un pied (12) de pale et/ou d'une bande de recouvrement (13) disposée dessus, est produite de manière générative.
  2. Système de pale de turbomachine selon la revendication précédente, caractérisé en ce que le corps est un corps d'impulsion (4) permettant de réduire les vibrations de la pale par de multiples contacts d'impact avec celle-ci.
  3. Système de pale de turbomachine selon l'une des revendications précédentes, caractérisé en ce que la zone de la pale produite de manière générative comporte une surface de contact (14) pour la mise en contact avec le corps (4).
  4. Système de pale de turbomachine selon l'une des revendications précédentes, caractérisé en ce que la zone de la pale (10) produite de manière générative, la zone du guide (50-52) produite de manière générative, la zone de la structure de support (6) produite de manière générative et/ou la zone du corps (4) produite de manière générative comporte du métal, est constituée en particulier de poudre métallique.
  5. Système de pale de turbomachine selon l'une des revendications précédentes, caractérisé en ce que le guide présente une cavité (51) ouverte ou fermée dans laquelle le corps (4) est disposé conjointement avec un jeu de mouvement.
  6. Système de pale de turbomachine selon la revendication précédente, caractérisé en ce qu'une dimension extérieure maximale du corps (4) est supérieure à une dimension intérieure maximale d'une ouverture de passage (52) d'une paroi (53) de la cavité ouverte (51) et/ou supérieure ou inférieure à un jeu de mouvement maximal.
  7. Système de pale de turbomachine selon l'une des revendications précédentes, caractérisé en ce que le corps (4), le guide (50) et/ou la structure de support (6) sont disposés dans une cavité (3), en particulier dans une cavité fermée, laquelle est définie au moins partiellement par la pale (10), en particulier par la zone de la pale produite de manière générative.
  8. Turbomachine, en particulier turbine à gaz, qui comporte au moins un système de pale de turbomachine selon l'une des revendications précédentes.
  9. Procédé de production d'un système de pale de turbomachine selon l'une des revendications précédentes, caractérisé en ce que la zone du guide (50), de la structure de support (6) et/ou du corps (4) conjointement avec la zone de la pale (10) est produite de manière générative.
EP17202370.7A 2016-11-21 2017-11-17 Système de pale de turbomachine Active EP3330485B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016222869.2A DE102016222869A1 (de) 2016-11-21 2016-11-21 Turbomaschinenschaufelanordnung

Publications (2)

Publication Number Publication Date
EP3330485A1 EP3330485A1 (fr) 2018-06-06
EP3330485B1 true EP3330485B1 (fr) 2020-04-29

Family

ID=60387936

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17202370.7A Active EP3330485B1 (fr) 2016-11-21 2017-11-17 Système de pale de turbomachine

Country Status (4)

Country Link
US (2) US20180142558A1 (fr)
EP (1) EP3330485B1 (fr)
DE (1) DE102016222869A1 (fr)
ES (1) ES2800172T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11898618B2 (en) 2021-05-20 2024-02-13 MTU Aero Engines AG Arrangement for reducing oscillation

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11118458B2 (en) 2017-10-27 2021-09-14 MTU Aero Engines AG Combination for sealing a gap between turbomachine blades and for reducing vibrations of the turbomachine blades
DE102018203093A1 (de) * 2018-03-01 2019-09-05 MTU Aero Engines AG Kombination zum Abdichten eines Spalts zwischen Turbomaschinenschaufeln und zum Reduzieren von Schwingungen der Turbomaschinenschaufeln
FR3092137B1 (fr) * 2019-01-30 2021-02-12 Safran Aircraft Engines Secteur de stator de turbomachine à zones soumises à des contraintes élevées
DE102019106734B4 (de) * 2019-03-18 2023-05-17 Man Energy Solutions Se Strömungsmaschinenrotor und Verfahren zum Herstellen desselben
IT202000026738A1 (it) * 2020-11-09 2022-05-09 Torino Politecnico Turbina a gas comprendente un elemento smorzatore di tipologia migliorata, e relativo elemento smorzatore
US11834960B2 (en) * 2022-02-18 2023-12-05 General Electric Company Methods and apparatus to reduce deflection of an airfoil

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1833751A (en) * 1929-07-05 1931-11-24 Gen Electric Vibration damping device
US2462961A (en) * 1945-01-24 1949-03-01 United Aircraft Corp Propeller blade vibration absorber
US2828941A (en) * 1952-12-24 1958-04-01 United Aircraft Corp Blade damping means
US2930581A (en) * 1953-12-30 1960-03-29 Gen Electric Damping turbine buckets
GB2093126B (en) * 1981-02-12 1984-05-16 Rolls Royce Rotor blade for a gas turbine engine
US6155789A (en) * 1999-04-06 2000-12-05 General Electric Company Gas turbine engine airfoil damper and method for production
US6827551B1 (en) * 2000-02-01 2004-12-07 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Self-tuning impact damper for rotating blades
US6607359B2 (en) * 2001-03-02 2003-08-19 Hood Technology Corporation Apparatus for passive damping of flexural blade vibration in turbo-machinery
US7736124B2 (en) * 2007-04-10 2010-06-15 General Electric Company Damper configured turbine blade
DE102009010185A1 (de) 2009-02-23 2010-08-26 Mtu Aero Engines Gmbh Gasturbinenmaschine
US9371733B2 (en) 2010-11-16 2016-06-21 Mtu Aero Engines Gmbh Rotor blade arrangement for a turbo machine
US8915718B2 (en) * 2012-04-24 2014-12-23 United Technologies Corporation Airfoil including damper member
US9121288B2 (en) * 2012-05-04 2015-09-01 Siemens Energy, Inc. Turbine blade with tuned damping structure
GB201210870D0 (en) * 2012-06-20 2012-08-01 Rolls Royce Plc Rotor balancing method
EP2806106A1 (fr) * 2013-05-23 2014-11-26 MTU Aero Engines GmbH Aube de turbomachine avec corps d'impulsion
US10914320B2 (en) * 2014-01-24 2021-02-09 Raytheon Technologies Corporation Additive manufacturing process grown integrated torsional damper mechanism in gas turbine engine blade
US9879551B2 (en) * 2014-05-22 2018-01-30 United Technologies Corporation Fluid damper and method of making
EP3018292B1 (fr) * 2014-11-10 2020-08-12 Ansaldo Energia Switzerland AG Aube rotorique de turbine, turbine à gaz et procédé de fabrication associés
DE102016204255A1 (de) * 2016-03-15 2017-09-21 Siemens Aktiengesellschaft Bauteil für eine Strömungsmaschine und Verfahren zu dessen Herstellung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11898618B2 (en) 2021-05-20 2024-02-13 MTU Aero Engines AG Arrangement for reducing oscillation

Also Published As

Publication number Publication date
US20180142558A1 (en) 2018-05-24
US20230003130A1 (en) 2023-01-05
EP3330485A1 (fr) 2018-06-06
ES2800172T3 (es) 2020-12-28
DE102016222869A1 (de) 2018-05-24

Similar Documents

Publication Publication Date Title
EP3330485B1 (fr) Système de pale de turbomachine
EP3191244B1 (fr) Procédé de production d'une aube mobile et aube obtenue
EP2663414B1 (fr) Procédé de fabrication générative d'un élément à système d'amortissement intégré pour turbomachine et élément à système d'amortissement intégré pour turbomachine fabriqué de façon générative
EP2737178B1 (fr) Procédé de fabrication, de réparation et/ou de remplacement d'un carter de propulseur, ainsi que carter correspondant
EP3231998B1 (fr) Segment d'une aube statorique
EP3219917B1 (fr) Agencement d'aubes de turbomachine, turbomachine et procédé de fabrication associés
EP2484870A1 (fr) Pale de turbomachine comprenant un elément d'amortissement et procédé de conception d'une telle turbomachine
EP3241995B1 (fr) Segment d'aube directrice pour une turbo-machine
EP3130757B1 (fr) Rotor de turbine à gaz à aubage
DE102010062087A1 (de) Strömungsmaschine mit Dichtstruktur zwischen drehenden und ortsfesten Teilen sowie Verfahren zur Herstellung dieser Dichtstruktur
EP2806105A1 (fr) Aube de turbomachine avec corps d'impulsion
EP3138996A1 (fr) Pale de turbocompresseur
EP3239461A1 (fr) Système de pale de turbomachine
DE102009052880A1 (de) Verfahren zum Herstellen eines integral beschaufelten Rotors, Vorrichtung zur Durchführung des Verfahrens sowie mittels des Verfahrens hergestellter Rotor
DE102013220983A1 (de) Laufschaufel für eine Turbomaschine
DE102016214234A1 (de) Laufschaufel mit Impulskörper
EP3196413B1 (fr) Étage de turbomachine
DE102006058678A1 (de) Verfahren und Vorrichtung zum Oberflächenstrahlen eines Teilelements eines Bauteils einer Gasturbine
EP2977554A1 (fr) Pales de turbomachine desaccordees
EP2860352A1 (fr) Rotor, procédé de manufacture et aube associés
WO2019030201A1 (fr) Structure fonctionnelle, composant correspondant pour une turbomachine et turbine
DE102015210014B4 (de) Gehäusestruktur einer Strömungsmaschine mit einem Bauteil mit gerichteter Mikrostruktur
EP3051063B1 (fr) Aube statorique à calage variable, turbo-machine et procédé de fabrication associés
EP3477048B1 (fr) Agencement d'étanchéité d'une interstice entre aubes de turbomachine et de réduction des vibrations des aubes de turbomachine
DE102019214667A1 (de) Komponente mit einem zu kühlenden Bereich und Mittel zur additiven Herstellung derselben

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20181116

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20191218

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1263601

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200515

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502017004966

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200429

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200729

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200829

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200831

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200730

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200729

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502017004966

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20210201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201117

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20201130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201117

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20201130

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1263601

Country of ref document: AT

Kind code of ref document: T

Effective date: 20221117

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20231123

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20231215

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20221117

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20231124

Year of fee payment: 7

Ref country code: DE

Payment date: 20231120

Year of fee payment: 7